Garmin GNS 530 User manual
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 1
0.1 RECORD OF REVISIONS
Rev.
No.
Reason Chap-
ter
Page(s) Date of
Revision
Approval Date of
Approval
Date Inserted Signature
1OÄM 40-117
WX 500
09-A21-1, 9-A21-2,
9-A21-3, 9-A21-4
15-Mar-2002
79-A21-33, 9-A21-34
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 2
0.2 LIST OF EFFECTIVE PAGES
Chapter Page Date
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DA 40 AFM Supplement A21
GNS 530
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89-A21-34 15 Mar 2002
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 1 15 Mar 2002 OÄM 40-117 Page 9 - A21 - 4
0.3 TABLE OF CONTENTS
Page
1. GENERAL ...............................................9-A21-5
2. OPERATING LIMITATIONS ..................................9-A21-5
3. EMERGENCY PROCEDURES ...............................9-A21-8
4A. NORMAL OPERATING PROCEDURES ........................9-A21-9
4B. ABNORMAL OPERATING PROCEDURES .....................9-A21-10
5. PERFORMANCE .........................................9-A21-11
6. MASS AND BALANCE .....................................9-A21-11
7. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ..........9-A21-11
8. AIRPLANE HANDLING, CARE AND MAINTENANCE .............9-A21-34|
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 5
1. GENERAL
This Supplement supplies the information necessary for the efficient operation of the
airplane when the COM/NAV/GPS GNS 530 is installed. The information contained
within this Supplement is to be used in conjunction with the complete AFM.
This Supplement is a permanent part of this AFM and must remain in this AFM at all
times when the GNS 530 is installed.
Refer to Section 7.14 for approved modes of operation (i. e. BRNAV, MNPS) of the
GNS 530´s GPS receiver.
2. LIMITATIONS
A. The GNS 530 Pilot's Guide, dated April 2000 or later appropriate revision must
be immediately available to the flight crew whenever navigation is predicated on
the use of the system.
B. The GNS 530 must utilize the following or later approved software versions:
Sub-System Software Version
Main 2.00
GPS 2.00
COMM 1.22
VOR/LOC 1.25
G/S 2.00
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 6
The Main software version is displayed on the GNS 530 self test page immediately
after turn-on for 5 seconds. The remaining system software versions can be verified
on the AUX group sub-page 2, 'SOFTWARE/DATABASE VER'.
C. IFR en route and terminal navigation predicated upon the GNS 530’s GPS
Receiver is prohibited unless the pilot verifies the currency of the data base or
verifies each selected waypoint for accuracy by reference to current approved
data.
D. Instrument approach navigation predicated upon the GNS 530’s GPS Receiver
must be accomplished in accordance with approved instrument approach
procedures that are retrieved from the GPS equipment data base. The GPS
equipment database must incorporate the current update cycle.
(1) Instrument approaches utilizing the GPS receiver must be conducted in
the approach mode and Receiver Autonomous Integrity Monitoring
(RAIM) must be available at the Final Approach Fix.
(2) Accomplishment of ILS, LOC, LOC-BC, LDA, SDF, MLS or any other
type of approach not approved for GPS overlay with the GNS 530’s GPS
receiver is not authorized.
(3) Use of the GNS 530 VOR/ILS receiver to fly approaches not approved
for GPS requires VOR/ILS navigation data to be present on the external
indicator.
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 7
(4) When an alternate airport is required by the applicable operating rules,
it must be served by an approach based on other than GPS or Loran-C
navigation, the aircraft must have the operational equipment capable of
using that navigation aid, and the required navigation aid must be
operational.
(5) VNAV information may be utilized for advisory information only. Use of
VNAV information for Instrument Approach Procedures does not
guarantee Step-Down Fix altitude protection, or arrival at approach
minimums in normal position to land.
E. If not previously defined, the following default settings must be made in the
'SETUP 1' menu of the GNS 530 prior to operation (refer to Pilot's Guide for
procedure if necessary):
(1) dis, spd: nm, kt (sets navigation units to 'nautical miles' and 'knots')
(2) alt, vs: ft, fpm (sets altitude units to 'feet' and 'feet per minute')
(3) map datum: WGS 84 (sets map datum to WGS-84, see note below)
(4) posn: hddd°mm.mmm' (sets navigation grid units to decimal minutes)
(5) fuel: gl (sets fuel units to gallons)
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 8
NOTE
In some areas datums other than WGS-84 may be used. If
the GNS 530 is authorized for use by the appropriate
Airworthiness authority, the required geodetic datum must
be set in the GNS 530 prior to its use for navigation.
F. The accuracy of the data base information is only assured if it is used before the
end of the effectivity period. Use of out of date data base information is done
entirely at the user´s own risk.
3. EMERGENCY PROCEDURES
A. If GNS 530 navigation information is not available or invalid, utilize remaining
operational navigation equipment as required.
B. If 'RAIM POSITION WARNING' message is displayed the system will flag and no
longer provide GPS based navigational guidance. The crew should revert to the
GNS 530 VOR/ILS receiver or an alternate means of navigation other than the
GNS 530’s GPS Receiver.
C. If 'RAIM IS NOT AVAILABLE' message is displayed in the en route, terminal, or
initial approach phase of flight, continue to navigate using the GPS equipment or
revert to an alternate means of navigation other than the GNS 530’s GPS
receiver appropriate to the route and phase of flight. When continuing to use
GPS navigation, position must be verified every 15 minutes using the GNS 530’s
VOR/ILS receiver or another IFR-approved navigation system.
DA 40 AFM Supplement A21
GNS 530
Doc. # 6.01.01-E Rev. 0 01 Dec 2001 Page 9 - A21 - 9
D. If 'RAIM IS NOT AVAILABLE' message is displayed while on the final approach
segment, GPS based navigation will continue for up to 5 minutes with approach
CDI sensitivity (0.3 nautical miles). After 5 minutes the system will flag and no
longer provide course guidance with approach sensitivity. Missed approach
course guidance may still be available with 1 nautical mile CDI sensitivity by
executing the missed approach.
E. In an in-flight emergency, depressing and holding the Comm transfer button for 2
seconds will select the emergency frequency of 121.500 MHz into the 'Active'
frequency window.
F. If GNS 530 Communication is inoperative, utilize remaining operational COMM
equipment (if installed) or follow standard communication failure procedure by
using Transponder Code 7600 and appropriate flight procedures.
4A. NORMAL PROCEDURES
DETAILED OPERATING PROCEDURES
Normal operating procedures are described in the GNS 530 Pilot's Guide, dated April
2000 or later appropriate revision.
PILOT'S DISPLAY
The GNS 530 System data will appear on the Pilot’s HSI. The source of data is either
GPS or VLOC as annunciated on the display above the CDI-key.
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